Browse TRAIL Inventories

Performance of air inlets at transonic and low supersonic speeds

Oxidation-resistance mechanism and other properties of molybdenum disilicide

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics

Normal accelerations and associated operating conditions on four types of commercial transport airplanes from VGH data available as of September 1951

Investigation of afterburner performance and afterburner fuel system coking of the Westinghouse XJ34-WE-32 engine

Preliminary investigation of a chemical starting technique for the acid - gasoline rocket propellant system

Preliminary investigation of corrosion by molten sodium hydroxide flowing in tubes of AISI 347 stainless steel, Inconel, and nickel having average outer-wall temperatures of 1500 F and a circumferential temperature gradient of 20 F

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Preliminary investigation of a rectangular supersonic scoop inlet with swept sides designed for low drag at a Mach number of 2.7

Preliminary free-flight investigation of the effects of rivets and lap joints on the drag of bodies at zero lift at supersonic Mach numbers to 2.1

A preliminary gust-tunnel investigation of leading-edge separation on swept wings

Preliminary experiments on the elastic compressive buckling of plates with integral waffle-like stiffening

Pressure distribution at low speed on a model incorporating a W wing with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section

Preparation and physical properties of metal slurry fuels

Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method

Lateral and directional dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Loitering and range performance of turbojet-powered aircraft determined by off-design engine cycle analysis

The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10

The longitudinal characteristics at Mach numbers up to 0.9 of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10

Low-speed aerodynamic characteristics of a large-scale 45 degree swept-back wing with partial-span slats, double-slotted flaps, and ailerons

Low-speed investigation of the effects of wing leading-edge modifications and several outboard fin arrangements on the static stability characteristics of a large-scale triangular wing

Ignition delay experiments with small-scale rocket engine at simulated altitude conditions using various fuels with nitric acid oxidants / Dezso J. Ladanyi

Free-spinning-tunnel investigation of a 1/30-scale model of the Grumman XS2F-1 airplane: TED No. NACA DE 366

Friction and surface damage of several corrosion-resistant materials

Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter Ram-jet engine / T. B. Shillito and Shigeo Nakanishi

Free-flight tests at Mach numbers from 0.8 to 1.4 to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a 45 degree sweptback wing having an NACA 65A009 airfoil

Measurements of thermal distortion of the submarine intermediate reactor "Mark A" moderator tube

Effect of current design trends on airplane spins and recoveries

Effect of fuel density and heating value on ram-jet airplane range

Correlation of buffet boundaries predicted from wind-tunnel tests with those measured during flight tests on the F8F-1 and X-1 airplanes -transonic-bump method

A Correlation by Means of the Transonic Similarity Rules of the Experimentally Determined Characteristics of 22 Rectangular Wings of Symmetrical Profile

Correlation of predicted and experimental lateral oscillation characteristics for several airplanes

Design and test of mixed-flow impellers 2: experimental results, impeller model MFI-1A

Design and test of mixed-flow impellers 1: aerodynamic design procedure

Design of apparatus for determining heat transfer and frictional pressure drop of nitric acid flowing through a heated tube

Effect of magnitude of vibratory load superimposed on mean tensile load on mechanism of and time to fracture of specimens and correlation to engine blade

Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades

An analytical study of the comparative performance of four air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 1.5

Analytical study of static and low-speed performance of thin propellers using two-speed gear ratios to obtain optimum rotational speeds

Comparison of calculated and experimental temperatures of water-cooled turbine blades

Combustion efficiency of homogeneous fuel-air mixtures in a 5-inch ram-jet-type combustor

Analysis of stage matching and off-design performance of multistage axial-flow compressors

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap

Characteristics of swept wings at high speeds

Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor

Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers


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